CN108513563A - Unmanned plane - Google Patents
Unmanned plane Download PDFInfo
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- CN108513563A CN108513563A CN201780005482.1A CN201780005482A CN108513563A CN 108513563 A CN108513563 A CN 108513563A CN 201780005482 A CN201780005482 A CN 201780005482A CN 108513563 A CN108513563 A CN 108513563A
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- horn
- unmanned plane
- driving mechanism
- main body
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- 230000007246 mechanism Effects 0.000 claims abstract description 114
- 230000000712 assembly Effects 0.000 claims description 5
- 238000000429 assembly Methods 0.000 claims description 5
- 230000005611 electricity Effects 0.000 claims description 5
- 230000001360 synchronised effect Effects 0.000 claims description 3
- 239000003086 colorant Substances 0.000 claims description 2
- 230000002045 lasting effect Effects 0.000 claims description 2
- 230000008450 motivation Effects 0.000 claims 1
- 238000011017 operating method Methods 0.000 abstract description 4
- 238000000034 method Methods 0.000 description 9
- 238000010586 diagram Methods 0.000 description 8
- 238000001514 detection method Methods 0.000 description 4
- 241000208340 Araliaceae Species 0.000 description 1
- 235000005035 Panax pseudoginseng ssp. pseudoginseng Nutrition 0.000 description 1
- 235000003140 Panax quinquefolius Nutrition 0.000 description 1
- 230000005540 biological transmission Effects 0.000 description 1
- 238000000354 decomposition reaction Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 235000008434 ginseng Nutrition 0.000 description 1
- 238000012856 packing Methods 0.000 description 1
- 238000002360 preparation method Methods 0.000 description 1
- 239000007787 solid Substances 0.000 description 1
- 230000000007 visual effect Effects 0.000 description 1
- 201000009482 yaws Diseases 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B60—VEHICLES IN GENERAL
- B60L—PROPULSION OF ELECTRICALLY-PROPELLED VEHICLES; SUPPLYING ELECTRIC POWER FOR AUXILIARY EQUIPMENT OF ELECTRICALLY-PROPELLED VEHICLES; ELECTRODYNAMIC BRAKE SYSTEMS FOR VEHICLES IN GENERAL; MAGNETIC SUSPENSION OR LEVITATION FOR VEHICLES; MONITORING OPERATING VARIABLES OF ELECTRICALLY-PROPELLED VEHICLES; ELECTRIC SAFETY DEVICES FOR ELECTRICALLY-PROPELLED VEHICLES
- B60L58/00—Methods or circuit arrangements for monitoring or controlling batteries or fuel cells, specially adapted for electric vehicles
- B60L58/10—Methods or circuit arrangements for monitoring or controlling batteries or fuel cells, specially adapted for electric vehicles for monitoring or controlling batteries
- B60L58/12—Methods or circuit arrangements for monitoring or controlling batteries or fuel cells, specially adapted for electric vehicles for monitoring or controlling batteries responding to state of charge [SoC]
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/32—Rotors
- B64C27/37—Rotors having articulated joints
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
- B64D27/02—Aircraft characterised by the type or position of power plants
- B64D27/24—Aircraft characterised by the type or position of power plants using steam or spring force
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D45/00—Aircraft indicators or protectors not otherwise provided for
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D47/00—Equipment not otherwise provided for
- B64D47/02—Arrangements or adaptations of signal or lighting devices
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/10—Rotorcrafts
- B64U10/13—Flying platforms
- B64U10/14—Flying platforms with four distinct rotor axes, e.g. quadcopters
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U30/00—Means for producing lift; Empennages; Arrangements thereof
- B64U30/20—Rotors; Rotor supports
- B64U30/29—Constructional aspects of rotors or rotor supports; Arrangements thereof
- B64U30/293—Foldable or collapsible rotors or rotor supports
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D45/00—Aircraft indicators or protectors not otherwise provided for
- B64D2045/0085—Devices for aircraft health monitoring, e.g. monitoring flutter or vibration
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U20/00—Constructional aspects of UAVs
- B64U20/80—Arrangement of on-board electronics, e.g. avionics systems or wiring
- B64U20/87—Mounting of imaging devices, e.g. mounting of gimbals
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T10/00—Road transport of goods or passengers
- Y02T10/60—Other road transportation technologies with climate change mitigation effect
- Y02T10/70—Energy storage systems for electromobility, e.g. batteries
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Remote Sensing (AREA)
- Life Sciences & Earth Sciences (AREA)
- Sustainable Development (AREA)
- Sustainable Energy (AREA)
- Power Engineering (AREA)
- Transportation (AREA)
- Toys (AREA)
Abstract
A kind of unmanned plane (1) includes fuselage main body (10) and is set to multiple horn components (201,202) of fuselage main body (10), and each horn component (201,202) includes the horn (221,222) for being connected to fuselage main body (10) and the driving mechanism (211,212) for driving horn (221,222) to rotate.Horn (221,222) includes unfolded state and folded state, each driving mechanism (211,212) drives corresponding horn (221,222) to be rotated relative to fuselage main body (10), and horn (221,222) is made to switch between unfolded state and folded state.The unmanned plane (1) drives horn (221,222) to automatically open or pack up by driving mechanism (211,212), simplifies the operating procedure of user, easily facilitates use.
Description
Technical field
The present invention relates to air vehicle technique field, more particularly to a kind of folding unmanned plane.
Background technology
Unmanned plane is used as tool of taking photo by plane most popular at present, and more and more consumers, which select unmanned plane to carry out shooting, to be made
With.To meet portability requirements of the user to nobody, a kind of unmanned plane of foldable horn is gradually appeared currently on the market, it is this
Foldable unmanned plane volume smaller after horn is packed up, occupies smaller space, is more convenient user and carries.
But user is in actual use, existing unmanned plane is required for user that horn is unfolded or is packed up, ability manually
Using or pack up unmanned plane, operating procedure is cumbersome.
Invention content
The present invention provides a kind of unmanned plane, including fuselage main body and the multiple horn components for being set to the fuselage main body,
Each horn component includes the horn for being connected to the fuselage main body and the driving machine for driving the horn rotation
Structure；The horn includes unfolded state and folded state, and each driving mechanism drives the corresponding horn relatively described
Fuselage main body rotates so that the horn switches between unfolded state and folded state.
The unmanned plane of the present invention drives horn to open or pack up by driving mechanism, to realize the horn of unmanned plane certainly
It is dynamic to open or pack up, the operating procedure of user is simplified, user's use of being more convenient for.
Description of the drawings
To describe the technical solutions in the embodiments of the present invention more clearly, make required in being described below to embodiment
Attached drawing is briefly described, it should be apparent that, drawings in the following description are only some embodiments of the invention, for
For those of ordinary skill in the art, without having to pay creative labor, it can also be obtained according to these attached drawings
His attached drawing.
Fig. 1 is the stereoscopic schematic diagram of a kind of unmanned plane in a folded configuration shown in one embodiment of the invention.
Fig. 2 is the decomposition diagram of unmanned plane shown in FIG. 1.
Fig. 3 is the stereoscopic schematic diagram of a kind of unmanned plane in the deployed state shown in one embodiment of the invention.
Fig. 4 is stereoscopic schematic diagram of a kind of unmanned plane in expansion/folding process shown in one embodiment of the invention.
Fig. 5 is the enlarged diagram at A in Fig. 2.
Fig. 6 is the upward view of unmanned plane shown in Fig. 3.
Fig. 7 is the enlarged diagram at B in Fig. 6.
Fig. 8 is the internal structure schematic diagram of unmanned plane shown in Fig. 3.
Fig. 9 is the enlarged diagram at C in Fig. 8.
Figure 10 and Figure 11 is the connection signal of the horn and driving mechanism of a kind of unmanned plane shown in one embodiment of the invention
Figure.
Specific implementation mode
Following will be combined with the drawings in the embodiments of the present invention, and technical solution in the embodiment of the present invention carries out clear, complete
Site preparation describes, it is clear that described embodiments are only a part of the embodiments of the present invention, instead of all the embodiments.It is based on
Embodiment in the present invention, it is obtained by those of ordinary skill in the art without making creative efforts every other
Embodiment shall fall within the protection scope of the present invention.
Example embodiments are described in detail here, and the example is illustrated in the accompanying drawings.Following description is related to
When attached drawing, unless otherwise indicated, the same numbers in different drawings indicate the same or similar elements.Following exemplary embodiment
Described in embodiment do not represent and the consistent all embodiments of the present invention.On the contrary, they be only with it is such as appended
The example of the consistent device and method of some aspects being described in detail in claims, of the invention.
It is the purpose only merely for description specific embodiment in terminology used in the present invention, is not intended to limit the invention.
It is also intended to including majority in the present invention and "an" of singulative used in the attached claims, " described " and "the"
Form, unless context clearly shows that other meanings.It is also understood that term "and/or" used herein refers to and wraps
Containing one or more associated list items purposes, any or all may be combined.
The present invention provides a kind of unmanned plane, including fuselage main body and the multiple horn components for being set to the fuselage main body,
Each horn component includes the horn for being connected to the fuselage main body and the driving machine for driving the horn rotation
Structure；The horn includes unfolded state and folded state, and each driving mechanism drives the corresponding horn relatively described
Fuselage main body rotates so that the horn switches between unfolded state and folded state.The unmanned plane of the present invention, passes through driving
Mechanism driving horn is opened or is packed up, and to realize that the horn of unmanned plane is automatically opened or packed up, simplifies the operation step of user
Suddenly, be more convenient for user use.
Below in conjunction with the accompanying drawings, the unmanned plane of the present invention is described in detail.In the absence of conflict, following implementation
Feature in example and embodiment can be combined with each other.
Shown in referring to Fig. 1 and Fig. 2, in an optional embodiment, unmanned plane 1 provided in an embodiment of the present invention, including machine
Body main body 10, multiple horn components 201,202, controller, battery 50 and holder device for shooting 60.In the present embodiment, more
A horn component 201,202 can be set to the side of the fuselage main body 10.
The top of fuselage main body 10 can be equipped with container 100, battery 50 be set in the container 100 and with the control
Device electrical connection processed, for powering to controller.Controller can be arranged in a motor plate 30, and motor plate 30 can be located at the receipts
In tank 100 and it is bonded the bottom for being set to the battery 50.Heat sink can be arranged in the bottom of the container 100, described
Heat sink fitting is set to the motor plate 30, plays the role of radiating for motor plate 30.
Holder device for shooting 60 can be set to the front of fuselage main body 10.The holder device for shooting 60 include holder holder and
It is equipped on the device for shooting of the holder holder.Optionally, the holder holder is three axis holder holders, and the holder holder includes
It yaws shaft assembly, the roll shaft assembly being flexibly connected with the yaw shaft assembly and is flexibly connected with the roll shaft assembly
Pitching shaft assembly, the device for shooting is equipped on the pitching shaft assembly.
The horn component 201,202 may include the horn 221 for being connected to the fuselage main body 10,222, driving mechanism
211,212 and rotor assemblies.Wherein, the driving mechanism 211,212 is electrically connected and can drive corresponding with the controller
Horn 221,222 relative to fuselage main body 10 rotate, to realize the portable functional of 1 foldable horn of unmanned plane.The rotation
Wing component includes the rotor (not shown) for being set to the motor 70 of horn 221,222 and being connected to motor 70, is driven by motor 70
Dynamic rotor rotational, to realize the flight function of unmanned plane 1.In the present embodiment, driving mechanism 211,212 is set to horn
221,222 one end, the motor 70 of the rotor assemblies are set to one far from driving mechanism 211,212 on horn 221,222
End, horn 221,222 are connect by corresponding driving mechanism 211,212 with fuselage main body 10.
Shown in Fig. 1 to Fig. 3, the machine for being used to indicate unmanned plane heading is also provided in the fuselage main body 10
Head indicator light 410, the electricity for being used to indicate the status indicator lamp 420 of drone status and being used to indicate 50 electricity of battery refer to
Show lamp 430.Optionally, LED light can be used in head indicator light 410, status indicator lamp 420 and battery capacity indication lamp 430.
In example shown in the figure, the head indicator light 410 is arranged in the horn of 10 front of fuselage main body
221, on 222, it is used to indicate the heading of unmanned plane, unmanned plane will show that red light is always on after starting, user is facilitated to carry out
Identification.The battery capacity indication lamp 430 is arranged on battery 50, and the quantity of battery capacity indication lamp 430 is four, battery capacity indication lamp 430
The quantity lighted is more, indicates that the electricity of battery 50 is higher.
The state that current unmanned plane is used to indicate at the rear portion of fuselage main body 10 is arranged in the status indicator lamp 420.Nobody
Machine can match combination remote controller and use, and GPS positioning system, vision system, alarm system, sensor and guide can also be arranged in inside
Needle etc., status indicator lamp 420 can dodge the lamp of different colours to show the different conditions of unmanned plane.For example, working as status indicator lamp
420 are continuously flickered with red greenish-yellow lamp, indicate System self-test.When status indicator lamp 420 is alternately flickered with yellow-green lamp, expression preheats.
When status indicator lamp 420 is with green light slow flash, expression uses GPS positioning.When status indicator lamp 420 is dodged so that green light is double, expression uses
Vision system positions.When status indicator lamp 420 is with amber light slow flash, no GPS no visuals positioning is indicated.When status indicator lamp 420 with
Green light quick flashing indicates brake.When status indicator lamp 420 is with amber light quick flashing, expression remote controller signal interrupts.Work as status indicator lamp
420, with red light slow flash, indicate low battery alarm.When status indicator lamp 420 is with red light quick flashing, serious low battery alarm is indicated.When
Status indicator lamp 420 indicates to place injustice or sensor error is excessive with red light interval flashing.When status indicator lamp 420 is with red
Lamp is always on, and indicates serious error.When status indicator lamp 420 is alternately flickered with reddish yellow lamp, expression compass error in data needs school
It is accurate.
Shown in Fig. 1 and Fig. 3, the horn 221,222 includes unfolded state and folded state.Unmanned plane 1 does not work
When, horn 221,222 is in folded state, and each horn 221,222 folds the side for being fitted in fuselage main body 10, such as Fig. 1 institutes
Show.When unmanned plane 1 works, horn 221,222 is in unfolded state, and each horn 221,222 is opened up with respect to fuselage main body 10 completely
It opens, as shown in Figure 3.The controller is used to send control signal to the driving mechanism 211,212, so that driving mechanism
211, the corresponding horn 221,222 of 212 drivings is rotated relative to the fuselage main body 10, realizes that horn 221,222 is being unfolded
Switch between state and folded state.It is shown in Figure 4, when horn 221,222 turns to unfolded state from folded state, each machine
Arm 221,222 is first fitted in the position of 10 side of fuselage main body along the direction far from fuselage main body 10 from folding as shown in Figure 1
Centre position as shown in Figure 4 is turned to, then gradually turns to the position that opposite fuselage main body 10 as shown in Figure 3 is fully deployed
It sets.When horn 221,222 turns to folded state from unfolded state, each horn 221,222 is first from opposite fuselage as shown in Figure 3
The position that main body 10 is fully deployed turns to centre position as shown in Figure 4 along close to the direction of fuselage main body 10, then gradually turns
It moves to folding as shown in Figure 1 and is fitted in the position of 10 side of fuselage main body.
By above-described embodiment it is found that the unmanned plane 1 of the present invention, is sent to driving mechanism 211,212 by controller and controlled
Signal drives corresponding horn 221,222 to open or pack up by driving mechanism 211,212, the horn 221 of realization unmanned plane 1,
222 automatically open or pack up, and increase the fun of using and degree of intelligence of product, simplify the operating procedure of user, be more convenient for
User uses, to improve the usage experience and the competitiveness of product in market of user.
In an optional embodiment, the control signal that controller is sent to driving mechanism 211,212 includes for controlling
The first signal that the driving mechanism 211,212 is rotated in a first direction, and then driving mechanism 211,212 is made to drive corresponding machine
Arm 221,222 is rotated in a first direction.In the present embodiment, driving mechanism 211,212 drives horn 221,222 along first direction
Rotation refers to that horn 221,222 turns to unfolded state from folded state, i.e., driving mechanism 211,212 drive horn 221,
222 rotate along the direction far from fuselage main body 10.After user starts unmanned plane 1 and Airplane detection success, the controller
It is synchronized to the multiple horn component 201,202 respective driving mechanisms 211,212 and sends first signal, so that multiple
Horn component 201,202 respective driving mechanisms 211,212 drive the opposite synchronization of fuselage main body 10 of corresponding horn 221,222 to turn
It moves to unfolded state.
In an optional embodiment, the control signal that controller is sent to driving mechanism 211,212 includes for controlling
The second signal that the driving mechanism 211,212 is rotated in a second direction, and then driving mechanism 211,212 is made to drive corresponding machine
Arm 221,222 is rotated in a second direction,.Wherein, the second direction is opposite to the first direction.In the present embodiment, it drives
Mechanism 211,212 drives horn 221,222 to be rotated in a second direction, and refers to that horn 221,222 turns to folding from unfolded state
State, i.e. driving mechanism 211,212 drive horn 221,222 to be rotated along close to the direction of fuselage main body 10.When user closes nothing
Man-machine 1 and Airplane detection success after, the controller to the multiple horn component 201,202 respective driving mechanisms 211,
212 synchronize the transmission second signal, so that the driving pair of multiple horn components 201,202 respective driving mechanisms 211,212
The relatively described fuselage main body 10 of the horn 221,222 answered is rotated synchronously to folded state.
In an optional embodiment, the unmanned plane 1 further includes the switch button 40 for opening and closing unmanned plane 1, this is opened
Button 40 is closed to be set on the battery 50 and be electrically connected with the controller.Start nobody when user presses the switch button 40
Machine 1, multiple horn components 201,202 respective driving mechanisms 211,212 drive corresponding horn 221,222 to open, Zhi Daozhuan
It moves to unfolded state.Unmanned plane 1, multiple horn components 201,202 respective drivings are closed when user presses the switch button 40
Mechanism 211,212 drives corresponding horn 221,222 to pack up, until turning to folded state.
In an optional embodiment, the horn component 201,202 further includes stopper section 231,232, the stopper section
231,232 it is set to the fuselage main body 10 along the rotation direction of the horn 221,222, the rotation direction refers to horn
221,222 direction for turning to unfolded state from folded state.When the horn 221,222 turns to expansion shape from folded state
When state, the horn 221,222 is connected to the stopper section 231,232, and stopper section 231,232 can be 221,222 to horn
To the effect of limit.When the horn 221,222 turns to folded state from unfolded state, the horn 221,222 is bonded
In the fuselage main body 10.
Further, the control signal that controller is sent to driving mechanism 211,212 includes for controlling the driving machine
The third signal that structure 211,212 is persistently rotated along first direction, so make driving mechanism 211,212 drive corresponding horn 221,
222 persistently rotate along first direction.When the horn 221,222 is in unfolded state, the controller is to the multiple machine
Arm component 201,202 respective driving mechanisms 211,212 send the third signal, so that multiple horn components 201,202
Respective driving mechanism 211,212 drives corresponding horn 221,222 to be connected to the stopper section with a lasting driving force
231,232, that is, after horn 221,222 turns to unfolded state, so that horn 221,222 is stopped by stopper section 231,232
Rotation stop is dynamic, but battery 50 still persistently can give driving mechanism 211,212 to power, and horn 221,222 is kept to provide certain torsion
Expansion torsion, avoid unmanned plane 1 in flight course or the case where horn 221,222 is accepted when being hit, directly
The switch button 40, which to be pressed, to user closes unmanned plane 1, controller sends the second signal to driving mechanism 211,212,
So that driving mechanism 211,212 drives corresponding horn 221,222 to pack up.
In an optional embodiment, the unmanned plane 1 is multi-rotor unmanned aerial vehicle.The multiple horn component 201,202
Including at least two first horn components 201 and at least two second horn components 202, described at least two first horn components
201 are set to the front of the fuselage main body 10, and described at least two second horn components 202 are set to the fuselage main body 10
Rear portion.
In the following, by taking unmanned plane 1 is quadrotor drone as an example, describe in detail to the unmanned plane 1 of the present invention.Its
In, the first horn component 201 is two, is symmetrically disposed on the front part sides of the fuselage main body 10.Second horn component 202 is
Two, it is symmetrically disposed on the rear portion both sides of the fuselage main body 10.
The first horn component 201 includes the first driving mechanism 211 for being set to 10 front of the fuselage main body, connection
It is set to fuselage main body 10 in the first horn 221 of the first driving mechanism 211 and along the rotation direction of the first horn 221
First stopper section 231.First driving mechanism 211 is connect with the controller, and the controller is to the first driving mechanism 211
Control signal is sent, so that the first driving mechanism 211 drives the first horn 221 to be rotated relative to fuselage main body 10.In this implementation
In example, vertical connection between the first driving mechanism 221 and the first horn 211 of the first horn component 201, the controller control
First driving mechanism 211 of the first horn component 201 vertically 910 rotation, so that the first driving mechanism 211 driving the
One horn 221 is relative to vertically 910 rotation of fuselage main body 10, that is, the first driving mechanism 211 drives the first horn
221 opposite fuselage main body, 10 front and back fold.
The second horn component 202 includes the second driving mechanism 212 for being set to 10 rear portion of the fuselage main body, connection
It is set to fuselage main body 10 in the second horn 222 of the second driving mechanism 212 and along the rotation direction of the second horn 222
Second stopper section 232.Second driving mechanism 212 is connect with the controller, and the controller is to the second driving mechanism 212
Control signal is sent, so that the second driving mechanism 212 drives the second horn 222 to be rotated relative to fuselage main body 10.In this implementation
In example, connection, the controller control are tilted between the second driving mechanism 212 and the second horn 222 of the second horn component 202
Second driving mechanism 212 of the second horn component 202,920 rotation in the horizontal direction, so that the second driving mechanism 212 driving the
Two horns 222 are relative to 920 rotation in the horizontal direction of fuselage main body 10, that is, the second driving mechanism 212 drives the second horn
222 opposite about 10 fuselage main bodies turn down.
Further, one end bottom that motor 70 is installed on the first horn 221 of the first horn component 201 is equipped with for institute
State the tripod 80 of the landing of unmanned plane 1.In order to avoid the first horn 221 and the second horn 222 are during opening or packing up, by
The case where normally can not opening or pack up to the influence of tripod 80, the controller can be according to specified sequence successively
Control instruction is sent to the first driving mechanism 211 and the second driving mechanism 212, so that the first horn 221 and the second horn 222
It opens or packs up successively according to specified sequence.
After user starts unmanned plane 1 and Airplane detection success, the controller is according to the first sequence successively to first
Driving mechanism 211 and the second driving mechanism 212 send first signal so that the first horn 221 and the second horn 222 according to
It is secondary to turn to unfolded state.In the present embodiment, first sequence is that the controller is first sent to the first driving mechanism 211
Signal is controlled, then control signal is sent to the second driving mechanism 212, i.e., the described controller is first sent to the first driving mechanism 211
First signal, then the first signal is sent to the second driving mechanism 212, and then the first driving mechanism 211 is made to drive the first horn 221
It first opens, the second driving mechanism 212 is opened after driving the second horn 222, prevents the second horn 222 from being beaten prior to the first horn 221
After opening, since tripod 80 is blocked by the second horn 222, and the case where cause the first horn 221 not open normally.
After user closes unmanned plane 1 and Airplane detection success, the controller is according to the second sequence successively to first
Driving mechanism 211 and the second driving mechanism 212 send the second signal so that the first horn 221 and the second horn 222 according to
It is secondary to turn to folded state.Wherein, second sequence is opposite with first sequence.In the present embodiment, described second is suitable
Sequence is that the controller first sends control signal to the second driving mechanism 212, then sends control letter to the first driving mechanism 211
Number, i.e., the described controller first sends second signal to the second driving mechanism 212, then sends the second letter to the first driving mechanism 211
Number, and then making the second driving mechanism 212 that the second horn 222 be driven first to pack up, the first driving mechanism 211 drives the first horn 221
After pack up, when preventing the first horn 221 from being packed up prior to the second horn 222, since tripod 80 is blocked by the second horn 222, and make
The case where can not normally being packed up at the first horn 221.
Shown in Figure 5 in an optional embodiment, the front side portion of the fuselage main body 10 is equipped with the first receiving portion
110, the first driving mechanism 211 of the first horn component 201 vertically 910 is installed in first receiving portion 110, the
First stopper section 231 of one horn component 201 for be located in the fuselage main body 10 front of first receiving portion 110 and with institute
The adjacent part in the first receiving portion 110 is stated to constitute.Shown in Figure 2, the rear lateral portion of the fuselage main body 10 is equipped with second and receives
Second driving mechanism 212 in appearance portion 120, the second horn component 202 is installed in the horizontal direction in second receiving portion 120,
Second stopper section 232 of the second horn component 202 is the portion for being located at second receiving portion, 120 top in the fuselage main body 10
Divide and extends outwardly.
Further, the first horn 221 includes the first side wall that is oppositely arranged and second sidewall, and the of the first horn 221
One side wall is equipped with the first abutting part 2214, and the second sidewall of the first horn 221 is equipped with the first sticking part 2215.When the first horn
221 when turning to unfolded state, and the first abutting part 2214 is connected to the first stopper section 231.When the first horn 221 turns to folding
When state, the first sticking part 2215 fits in fuselage main body 10.Second horn 222 includes the first side wall and second being oppositely arranged
The first side wall of side wall, the second horn 222 is equipped with the second abutting part 2222, and the second sidewall of the second horn 222 is supported equipped with third
Socket part 2223, between its first side wall and second sidewall and close to the third side wall of fuselage main body 10 on the second horn 222
Equipped with the second sticking part 2224.When the second horn 222 turns to unfolded state, the second abutting part 2222 is connected to the second backstop
Portion 232.When the second horn 222 turns to folded state, third abutting part 2223 is connected to the second stopper section 232, the second patch
Conjunction portion 2224 fits in fuselage main body 10.
Shown in Figure 2 in an optional embodiment, the first driving mechanism 211 is driving motor, the first horn 221
End be equipped with the first mounting portion 2211, first mounting portion 2211 be installed in the first receiving portion 110 and with the first driving machine
Structure 211 connects.Further, shown in Figure 5, the first driving mechanism 211 includes first motor main body 2111 and is set to
First drive shaft 2112 and the first mounting plate 2113 at 2111 both ends of first motor main body, the receiving of the first mounting plate 2113 and first
The side wall in portion 110 is affixed, and the first drive shaft 2112 vertically 910 is extended, and affixed with the first mounting portion 2211.The
The side wall of one receiving portion 110 is equipped with first through hole 111 and the first mounting hole 112, and the first mounting plate 2113 is equipped with and the first peace
Fill 112 corresponding first connecting hole 2114 of hole.Shown in Fig. 6 and Fig. 7, first motor main body 2111 is arranged in first through hole
111, the first mounting plate 2113 is (excellent by the first fastener 2115 for being arranged in the first connecting hole 2114 and the first mounting hole 112
It is selected as bolt) it is affixed with the side wall of the first receiving portion 110.Certainly, it is logical can not also to be arranged first for the side wall of the first receiving portion 110
Hole 111, first motor main body 2111 are directly affixed by the first fastener 2115 and 110 side wall of the first receiving portion.
Shown in Figure 2, the second driving mechanism 212 is driving motor, and the end of the second horn 222 is equipped with the second mounting portion
2221, which is installed in the second receiving portion 120 and is connect with the second driving mechanism 212.Further,
Two driving mechanisms 212 include the second motor body 2121 and the second drive shaft for being set to 2121 both ends of the second motor body
2122 and second mounting plate 2123, the second mounting plate 2123 and the bottom wall of the second receiving portion 120 are affixed, 2122 edge of the second drive shaft
Second axial 920 is extended, and affixed with the second mounting portion 2221.The bottom wall of second receiving portion 120 is equipped with the second through-hole 121
With the second mounting hole 122, the second mounting plate 2123 is equipped with second connecting hole corresponding with the second mounting hole 122 2124.Ginseng
See shown in Fig. 8 and Fig. 9, the second motor body 2121 is arranged in the second through-hole 121, and the second mounting plate 2123 is by being arranged in second
The second fastener 2125 (preferably bolt) and the bottom wall of the second receiving portion 120 of connecting hole 2124 and the second mounting hole 122 are solid
It connects.Certainly, the second through-hole 121 can not also be arranged in the bottom wall of the second receiving portion 120, and the second motor body 2121 directly passes through
Two fasteners 2125 and the bottom wall of the second receiving portion 120 are affixed.
Shown in Figure 10 and Figure 11, the first mounting portion 2211 of the first horn 221 is equipped with and first motor main body 2111
Compatible first host cavity 2212, the bottom wall of the first host cavity 2212 are equipped with compatible with the first drive shaft 2,112 second and receive
Vessel 2213.First motor main body 2111 is contained in the first host cavity 2212, and the first drive shaft 2112 is contained in the second receiving
It is in chamber 2213 and affixed with the first mounting portion 2211.In this way, the appearance of the first driving mechanism 211 and the first horn 221 can be made
It is smooth, to save space.Similarly, the second mounting portion 2221 of the second horn 222 is equipped with suitable with 2121 phase of the second motor body
The bottom wall of the third host cavity (not shown) matched, the second accommodating cavity is equipped with the 4th host cavity compatible with the second drive shaft 2122
(not shown).Second motor body 2121 is contained in third host cavity, and the second drive shaft 2122 is contained in the 4th host cavity
And it is affixed with the second mounting portion 2221.In this way, the can be made and the flat appearance of driving mechanism 212 and the second horn 222, with section
About space.
It should be noted that herein, relational terms such as first and second and the like are used merely to a reality
Body or operation are distinguished with another entity or operation, are deposited without necessarily requiring or implying between these entities or operation
In any actual relationship or order or sequence.The terms "include", "comprise" or its any other variant are intended to non-row
His property includes, so that the process, method, article or equipment including a series of elements includes not only those elements, and
And further include other elements that are not explicitly listed, or further include for this process, method, article or equipment institute it is intrinsic
Element.In the absence of more restrictions, the element limited by sentence "including a ...", it is not excluded that including institute
State in the process, method, article or equipment of element that there is also other identical elements.
It is provided for the embodiments of the invention unmanned plane above to be described in detail, specific case pair used herein
The principle of the present invention and embodiment are expounded, and the explanation of above example is only intended to help to understand core of the invention
Thought；Meanwhile for those of ordinary skill in the art, according to the thought of the present invention, in specific implementation mode and application range
Upper there will be changes, in conclusion the content of the present specification should not be construed as limiting the invention.
Claims (25)
1. a kind of unmanned plane, which is characterized in that including fuselage main body and the multiple horn components for being set to the fuselage main body, often
A horn component includes the horn for being connected to the fuselage main body and the driving mechanism for driving the horn rotation；
The horn includes unfolded state and folded state, and each driving mechanism drives the corresponding relatively described fuselage of the horn
Body rotation so that the horn switches between unfolded state and folded state.
2. unmanned plane according to claim 1, which is characterized in that further include the control being electrically connected with each driving mechanism
Device processed, for sending control signal to the driving mechanism, so that the driving mechanism drives the corresponding horn opposite
The fuselage main body rotation.
3. unmanned plane according to claim 2, which is characterized in that the control signal includes for controlling the driving machine
The first signal that structure is rotated in a first direction；
When the unmanned plane starts, the controller is synchronized to the respective driving mechanism of the multiple horn component sends described the
One signal, to drive the multiple relatively described fuselage main body of the respective horn of horn component to rotate synchronously to unfolded state.
4. unmanned plane according to claim 3, which is characterized in that the control signal further includes for controlling the driving
The second signal that mechanism is rotated in a second direction, the second direction are opposite to the first direction；
When the unmanned plane is closed, the controller is synchronized to the respective driving mechanism of the multiple horn component sends described the
Binary signal, to drive the multiple relatively described fuselage main body of the respective horn of horn component to rotate synchronously to folded state.
5. unmanned plane according to claim 2, which is characterized in that the horn component further includes stopper section, the backstop
Portion is set to the fuselage main body along the rotation direction of the horn；
When the horn is unfolded state, the horn is connected to the stopper section；When the horn is folded state, institute
It states horn and fits in the fuselage main body.
6. unmanned plane according to claim 5, which is characterized in that the control signal includes for controlling the driving machine
The third signal that structure is persistently rotated along first direction；
When the horn is unfolded state, the controller sends the third signal to the driving mechanism, to drive
It states horn and the stopper section is connected to a lasting driving force.
7. unmanned plane according to claim 5, which is characterized in that the multiple horn component includes at least two first machines
Arm component and at least two second horn components, before described at least two first horn components are set to the fuselage main body
Portion, described at least two second horn components are set to the rear portion of the fuselage main body.
8. unmanned plane according to claim 7, which is characterized in that the control signal includes for controlling first machine
The first signal that the driving mechanism of arm component and the driving mechanism of the second horn component are rotated in a first direction；
When the unmanned plane starts, the controller according to the first sequence successively to the driving mechanism of the first horn component and
The driving mechanism of the second horn component sends first signal, to drive the horn of the first horn component and described
The horn of second horn component turns to unfolded state successively.
9. unmanned plane according to claim 8, which is characterized in that the control signal further includes for controlling described first
The second signal that the driving mechanism of horn component and the driving mechanism of the second horn component are rotated in a second direction, described
Two directions are opposite to the first direction；
When the unmanned plane is closed, the controller according to the second sequence successively to the driving mechanism of the first horn component and
The driving mechanism of the second horn component sends the second signal, to drive the horn of the first horn component and described
The horn of second horn component turns to folded state successively；Wherein, second sequence is opposite with first sequence.
10. unmanned plane according to claim 9, which is characterized in that first sequence is the controller first to described
The driving mechanism of first horn component sends control signal, then sends control letter to the driving mechanism of the second horn component
Number；Second sequence is that the controller first sends control signal to the driving mechanism of the second horn component, then to institute
The driving mechanism for stating the first horn component sends control signal.
11. unmanned plane according to claim 7, which is characterized in that the driving mechanism and horn of the first horn component
Between vertical connection, the driving mechanism that the controller controls the first horn component vertically rotates；
Connection is tilted between the driving mechanism and horn of the second horn component, the controller controls the second horn group
The driving mechanism of part rotates in the horizontal direction.
12. unmanned plane according to claim 11, which is characterized in that the front side portion of the fuselage main body is equipped with the first receiving
The driving mechanism in portion, the first horn component is installed in first receiving portion, the stopper section of the first horn component
To be located in the fuselage main body in front of first receiving portion and being constituted with the adjacent part in first receiving portion；
The rear lateral portion of the fuselage main body is equipped with the second receiving portion, and the driving mechanism of the second horn component is installed in described the
In two receiving portions, the stopper section of the second horn component is the portion being located in the fuselage main body above second receiving portion
Divide and extends outwardly.
13. unmanned plane according to claim 2, which is characterized in that further include the battery for powering to the controller,
The top of the fuselage main body is equipped with container, and the battery is set in the container and is electrically connected with the controller.
14. unmanned plane according to claim 13, which is characterized in that further include for open and close the switch of the unmanned plane by
Button is set on the battery and is electrically connected with the controller.
15. unmanned plane according to claim 13, which is characterized in that the controller is set to a motor plate, the electricity
Machine plate is bonded the bottom for being set to the battery.
16. unmanned plane according to claim 15, which is characterized in that the bottom of the container is equipped with heat sink, described
Heat sink fitting is set to the motor plate.
17. unmanned plane according to claim 13, which is characterized in that further include the machine for being used to indicate unmanned plane heading
Head indicator light, is set to the front of the fuselage main body.
18. unmanned plane according to claim 13, which is characterized in that further include the electricity for being used to indicate the battery capacity
Indicator light is set on the battery.
19. unmanned plane according to claim 13, which is characterized in that further include being used to indicate the state of drone status to refer to
Show lamp, is set to the rear portion of the fuselage main body；The status indicator lamp dodges the lamp of different colours to show the difference of unmanned plane
State.
20. unmanned plane according to claim 1, which is characterized in that the multiple horn component is set to the fuselage master
The side of body.
21. unmanned plane according to claim 1, which is characterized in that further include holder device for shooting, be set to the fuselage master
The front of body, the holder device for shooting include holder holder and are equipped on the device for shooting of the holder holder.
22. unmanned plane according to claim 21, which is characterized in that the holder holder is three axis holder holders, described
Holder holder include yaw shaft assembly, with it is described yaw the roll shaft assembly that is flexibly connected of shaft assembly and with the roll axis
The pitching shaft assembly of component flexible connection, the device for shooting are equipped on the pitching shaft assembly.
23. unmanned plane according to claim 1, which is characterized in that the horn component further includes rotor assemblies, the drive
Motivation structure is set to one end of the horn, and the rotor assemblies are set to one far from the driving mechanism on the horn
End.
24. unmanned plane according to claim 23, which is characterized in that the rotor assemblies include being set to the motor of horn
With the rotor for being connected to the motor, the motor is set to one end far from the driving mechanism on the horn.
25. unmanned plane according to claim 1, which is characterized in that the bottom of the horn, which is equipped with, is used for the unmanned plane
The tripod of landing.
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| PCT/CN2017/099700 WO2019041174A1 (en) | 2017-08-30 | 2017-08-30 | Unmanned aerial vehicle |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN108513563A true CN108513563A (en) | 2018-09-07 |
| CN108513563B CN108513563B (en) | 2021-12-21 |
Family
ID=63375230
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201780005482.1A Expired - Fee Related CN108513563B (en) | 2017-08-30 | 2017-08-30 | Unmanned plane |
Country Status (3)
| Country | Link |
|---|---|
| US (1) | US20200164957A1 (en) |
| CN (1) | CN108513563B (en) |
| WO (1) | WO2019041174A1 (en) |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109278981A (en) * | 2018-11-16 | 2019-01-29 | 华东理工大学 | A kind of miniature foldable three-dimensional live modeling unmanned plane |
| WO2021043334A1 (en) * | 2019-09-03 | 2021-03-11 | 深圳市道通智能航空技术有限公司 | Unmanned aerial vehicle |
| CN112896488A (en) * | 2021-02-26 | 2021-06-04 | 深圳市道通智能航空技术股份有限公司 | Method for controlling unmanned aerial vehicle and unmanned aerial vehicle |
| CN113859512A (en) * | 2020-06-30 | 2021-12-31 | 广东世季科技有限公司 | Portable unmanned aerial vehicle folding arm structure |
| CN114313212A (en) * | 2022-01-26 | 2022-04-12 | 西南石油大学 | Miniature unmanned aerial vehicle that can fold automatically and expand |
| WO2022096012A1 (en) * | 2020-11-09 | 2022-05-12 | 影石创新科技股份有限公司 | Unmanned aerial vehicle |
| US12071237B2 (en) * | 2016-02-22 | 2024-08-27 | SZ DJI Technology Co., Ltd. | Foldable multi-rotor aerial vehicle |
Families Citing this family (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| USD814970S1 (en) | 2016-02-22 | 2018-04-10 | SZ DJI Technology Co., Ltd. | Aerial vehicle |
| WO2017147764A1 (en) * | 2016-02-29 | 2017-09-08 | 深圳市大疆创新科技有限公司 | Power supply component, unmanned aerial vehicle and remotely controlled moving device |
| US11136136B2 (en) * | 2017-11-30 | 2021-10-05 | Textron Innovations Inc. | System and method for flight mode annunciation |
| WO2019140658A1 (en) * | 2018-01-19 | 2019-07-25 | 深圳市大疆创新科技有限公司 | Heat dissipation structure, heat dissipation method and device, unmanned aerial vehicle and readable storage medium |
| CN110254688B (en) * | 2019-06-27 | 2021-06-15 | 江苏大成航空科技有限公司 | Agricultural folded cascade plant protection unmanned aerial vehicle |
| CN110844058B (en) * | 2020-01-06 | 2023-01-24 | 天津中德应用技术大学 | Modular morphing aircraft |
| CN112740468A (en) * | 2020-03-02 | 2021-04-30 | 深圳市大疆创新科技有限公司 | Locking assembly and movable platform |
| CN215098210U (en) * | 2021-05-31 | 2021-12-10 | 上海峰飞航空科技有限公司 | Arm and unmanned aerial vehicle |
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| US12071237B2 (en) * | 2016-02-22 | 2024-08-27 | SZ DJI Technology Co., Ltd. | Foldable multi-rotor aerial vehicle |
| CN109278981A (en) * | 2018-11-16 | 2019-01-29 | 华东理工大学 | A kind of miniature foldable three-dimensional live modeling unmanned plane |
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| CN113859512A (en) * | 2020-06-30 | 2021-12-31 | 广东世季科技有限公司 | Portable unmanned aerial vehicle folding arm structure |
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| CN112896488A (en) * | 2021-02-26 | 2021-06-04 | 深圳市道通智能航空技术股份有限公司 | Method for controlling unmanned aerial vehicle and unmanned aerial vehicle |
| CN114313212A (en) * | 2022-01-26 | 2022-04-12 | 西南石油大学 | Miniature unmanned aerial vehicle that can fold automatically and expand |
Also Published As
| Publication number | Publication date |
|---|---|
| WO2019041174A1 (en) | 2019-03-07 |
| US20200164957A1 (en) | 2020-05-28 |
| CN108513563B (en) | 2021-12-21 |
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